STC SA6073NM

This Certificate issued to Structural Integrity Engineering 9525 Vassar Avenue Chatsworth, California 91311 Part 23* of the Federal Aviation Regulations. *For certification basis see T. C. Data Sheet A14CE Original Product Type Certificate Number :

A14CE Beechcraft 99, 99A, A99A, B99 and C99 Description of Type Design Change: Installation of fatigue sensor and structural life extension of wing spar in accordance with FAA approved SIE Master Drawing List 91000, Revision A, dated September 23, 1993, or later FAA approved revision, and FAA approved Airplane Flight Manual Supplement Report No. SIE-12-601, Revision N/C, dated October 19, 1993 or later FAA approved Airplane Flight Manual Supplement, and Report No. SIE-12-602, Revision N/C, dated December 21, 1993, or later FAA approved Revision. (SIE-12-601 is for model C99 only, and SIE-12-602 is for the remaining models, 99, 99A, A99A, and B99.)

Limitations and Conditions: This installation should not be extended to other aircraft of this model on which other previously approved modifications are incorporated unless it is determined that the installer that the interrelationship between this change and any of those other previously approved modifications will produce no adverse effect upon the airworthiness of that airplane. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission.

Date of application : September 1, 1992

Date of issuance : November 15, 1993

Date reissued : December 29, 2003

Date amended : December 30, 1993

( Signature) Manager, Technical & Administrative Support Staff, Los Angeles Aircraft Certification Office ( Title)

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Number SA6073NM

Limitations and Conditions (Cont.)

NOTES 3, Page 17 of the Type Certification Data Sheet No. A14CE for Beechcraft 99 Airliner Series, dated March 15, 1992, references the Pilot’s Operating Handbook and FAA Approved Flight Manual (as noted below*), Limitation Section for the mandatory retirement times for all Beech 99 Airliner Series structural components except as outlined in the FAA Approved Structural Integrity Engineering Airplane Flight Manual Supplement Report No. 12-601, Revision N/C, dated October 19, 1993, or later FAA approved revisions for C99’s, and the FAA Approved Structural Integrity Engineering Airplane Flight Manual Supplement Report No 12-602, Revision N/C dated December 21, 1993, or later FAA Approved revision for the 99’s, 99A’s, A99A’s, and B99’s.

Structural Integrity Engineering Instructions for Continued Airworthiness, Report No. 12-701, Revision A, dated November 9, 1993, provides the necessary maintenance and inspection information and is a part of this STC.

* Beechcraft PN #99-590012-3C issued January 31, 1973, or later revision for model 99’s

Beechcraft PN #99-590019-3C issued April 2, 1973, or later revision for model 99A’s

Beechcraft PN #99-590023-3 issued February 5, 1971, or later revision for model A99A’s

Beechcraft PN #99-590026-3A9 issued March 13, 1972, or later revision for model B99’s

Beechcraft PN #99-590030-3 issued July, 1981, or later revision for model C99’s.

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